Air brake



Dec. 26, 1933. H. E. HONEYWELL AIR BRAKE Patented Dec. 26, 1933 E. Hon ywell, Clayton, ffMo.. f

shell -isV-completelvclosed except atnits rearl end and the, open: rear endfoffsa'id shell isprovided with a` closure 6 connected with; the shell. 5 by ai hinge '7,V which. permits' said closureto be closed, as. shown inFigs. 1 and' 5, .or opened,` as shown in Figs. 23 and 4'of'the drawing. Iheishell 5 This invention relates. to air brakesi'and has special reference to devices for.use:in. connection with aircraft' to check and'V reducezthe speed of travel of the aircraft during emergencies .ordur- .inglandingand is valso useful as an aidto .the pilot in Aregaining control ofhthe aircraft as,.for instanace;duringtailspin. a. An objectofthe inventionpisto provide-.an improved device for use in connection kwith'air-v Vcraftand means-for operating and controlling said device whereby said device maybe caused to function'aszabrake or retarder to reduce the speed of flight-or descentofftheaircraft, thus Aenabling thepilot to stop within a shorter distance or-to regain controlflof'the aircraft before a crash occurs. l' 1 i "'Anotherobject :of theinvention is toprovide means Yfor disabling thedevice after it hasp'erformed itsintended function, so that said device -gage and operate said will no longer retard the flight of .the aircraft; and also to provide means forreconditioning .thede vice tofperform itsfunction. V

Other objects will appear fromthe following description,` reference beingl made tothe accompanying drawing, in which; f y l '.1 x

A Fig. 1 is' a-plan view ofj an airplane showing the invention'in connection therewith. Y .Y 'f

Fig. 2 isa similar View showing vth beginning 4to-functi'on as abrake or retarder for the airplane. J y 'Y n Fig.' 3. is a similar view-showing 'the device functioning as alorakevr or retardersfor'thevair plane.

Fig. 4 is a similar view showing the device disabled or conditioned,so thatitwill notretard the flight of the airplane. I

Fig. 5'is a sectionalview showing thehousing within which the'device is stored Ywhen not in l parachute and includi USB.

Figf is a'sidefelevation Ofthendevicethat controls the f unctioning'of'the air brakeor iretarder. v .f a

Fig. 7 isa sec`tionalview of the device shownA inFig.'6.

fi. Fig. 8^is .ap'rspective view of a detail of the invention. i j ;y f The Aairplane thatis-shown diagrammatically in Figs. 1 to 4, inclusiveicomprises the .usual fuselage 1, wings 2, vstabilizer 3 and pilot.cock pit 4. y. Y

Y' Asheu casingt is attached to some fixed part Y of the airplane `andjforconvenience of illustra-v` tion isV shownfattached to the stabilizeryalthou'ghl-it is to beunderstood that this shell may; j be mounted in anylappropriateposition. iThe. v

' f inventionA and'theclosure 6 have abuttingextensions 8. providedwith holes throughA which v the fastener 9 may be' extended to -hold the. closure in closed po-L holes in fthe extensions sition.l The fastener '9 is shownas a-cotter pnj having its stem passing rearwardly; through ,the

the stem Vspread apart so as tohold the Vcotter pin infposition. and yet. pe withdrawn forwardly. Y

rmit s aidA .cotter pin to .be A linkA 1 0 has zits rear end pivoted to the cotterpin 9 and its forward yend pivoted to a leverqll.:` The lever 1-1 ismounted on apivot, 12 located in the cockpittgadjaent to draw cthe Cotter pin 9 lever 11.-.and `quickly with.- from its yengagement with the extension 8` andthus quickly` release the closure and permit the air brake orretarder .to be ejected fromthe shell. f

Anfejector spring 13fis mountedfwithin the shell 5 Tand is compressed when the retarder is Within `said shell, ;so that when-the `closure 6 is expands, and immediately ejectsthe brake or retarder from vtheshell 5. A

opened the spring l13 similar l.sprir1g14 issecuredwithin ther closure 6 and.. presses ragainst the adjacent endy ofithe re-L' tarder or brake andthereby cooperates` to store upgenergy.- in thev springA v13, s o that said spring Al3--willfquickly-l expand and .eject the-brake or retarder :fromf the shell in theintended manner.

.'In .the embodiment the brake or retarder c Offthg. invention shown., omprises a number of elementssomewhatsimilar to an-.urnbrella orto a front,- the ielement'; 16

ment' 15 andpof largerareaand the element 1T.

rearwardly from the element 16 and of .larger whichifextends intothe' element 16g whenfthe device is in use -soias to Ypermitair to pass through the hole ,atthecenterof the elementl and thencev through the tube 18 and against the centerof the element 1 6. SimilarlyV the'elementV .16 has a central hole opening into an' attached element 1'7 adjacent .to ,the v lcentral vhole 204 through vsaid'elernent 17- to'vexpedite rthe opening. andfunctioning of saidlelements.;

meiner feas y2li-f element 17 around theopening 20.

tached to the marginal portions of the element 17. These cords extend forwardly through eyelets 22 on the marginal portion of the element 16 and through eyelets 23 on the marginal por-V tions' of the element 15. Thus, these cords converge forwardly and have their forward ends attached to a uniting member or body 24. The cords 21 have knots or knobs 21a to abut against the rear of the eyelets 22 and 23 to hold the elements^15 and 16 in umbrella form.` From the uniting member or body 24, a cord or kcable 25 extends forwardly to connection with a reel 26 on which the cord or cable 25 may be wound.` The reel 26 is mounted on an axial support 27 and is frictionally clamped between an abutment 28 and a plate 29, a nut 30 being screwed on the axle 27 to obtain this clamping arrangement. A strong spring 31 Vis mounted within the' reel 26 having one end attached to the axle 2,7 and the other end attached to the reel in a manner such that when thecord or cable 25 `is pulled toward the rear, the reel 26 will be turned in a direction to place the spring 3l under tension, to prevent backlash and to return the elements 15, 16 and-17 to open position preparatory to being rolled up and placed in the shell 5.

' A cord or cable 32 has a bifurcated portion 33 at its rear endvattached to the margin of the y This cord or cable 32 extendsforwardly'through the tubes 19 and 18 and through the body 24 to connection with a part 34 that'is rigid with the airplane, and has bifurcated portions 32a connected with A the margins of the elements 15 and 16 around the central holes in said elements.

A lock is mounted on a pivot 36 and hasan end 37 pressed -into contact with the periphery of a circumferential flange 38 on the reel 26 and arranged to engage in a notch 39 in said flange. A spring 40 has one end seated against the lock 35 and the opposite end against an abutment 41 on the end of a screw 42 mounted in a bracket 43 and adjustable to vary the tension of said spring 40. When the cord or cable 25 is woundon the reel 26-to prevent rearward sliding movement of the'body 24 along Ythe cord or cable 32, the body 24 is held in a position in which the elements 15, 16'and 1-7 will positively be held insubstantially the relationship shown in Fig. 3 of the drawing, presentingconcave surfaces `toward the rear end of the airplane to catch the air and thus retard the speed of movement of the airplane. VThis effective function'ofrthe cord 25 in cooperation with the reel 26 may be described -aspreventing f the elements 15, 16 and 17 fromturning inside 17 and thus permit the marginal portions of said elementsrto fold and extend'rearwardly and assume `ineffective positions by turning inside out in the manner suiciently shown in Fig. 4 of the drawing and remainso at will vof the operator- 'lil' pilot.

A fixed part of the airplane adjacent to the casing 5 supports a bracket 45 over which the cords or cables25 and 32 extend. A cotter pin 46 is normally mountedainvthe bracket 45 and holds the cords or cables 25 and 32 from rising.v

When it is desired to permit the cords or cables 25 and 32 to rise vertically from the reel 26 and the part 34, the lever 11 is moved an additional distance beyond which it had been moved to release the cotter pin 9. This additional movement of the lever 11 takes up a slack in the connection 47 between the link 10 and the pin 46 and withdraws said pin 46 from the bracket 45. This disconnects the cords or cables 25 and 32 from the rear end of the airplane and permits them to extend upwardly as described.

Normally, and when this device is not in use, it

vis rolled upon itself beginning at the rear end of the device and rolling it forwardly to the shell 5. The device being composed of thin and durable material occupies comparatively little space and is receivable in the shell 5 as shown and described. The device is kept in the shell until an emergency demanding the use of the device arises, such, for instance, as the airplane going into a tailspin; or until lit may be Adesired to vuse the device in landing orY for some other purpose. When the need to use the ,device arises, it is only necessary to -operate the lever 11 a distance suincient to detach the cotter pin 9 from the'extenf" sions v3 and thus permit the spring 13V to Vact to eject the device from the shell 5. ,Since the air.-v plane isin motion, the ejected device extendsto the rear and unrolls, as will be understood Mby reference to Fig. 2 of the drawing, and eventually opens, as shown in Fig. 3, thus effectively retard; ing the speed of iiight of theairplane or retarding aitailspin until the `pilot can regain control. f After the need for useof the device has ended, the lock 35 is released from the reel 26, permitting the device to assume an ineffectiveposition by permitting the elements 15, 16 and 17 to turn inside out and thus present no substantial re.- sistance to the travel-of `the airplane. After the devicehas thus beenl used andY at the opportune time, it is again rolled up vandplaced Within the shell 5. ,Y j

A crank 48 is releasably engageable with the iis axle 27 to rotate said` axle to tensionor unwindv the spring .31 whenever it may be advisable to ldo so; and to restore the elements l5, 16 and 17 to the positions and adjustments shown in Fig. 3.

`The construction and arrangement of the ele-y ments of this device may be varied substantiaily within equivalent limits without departure from the scope and principle ,of the invention. VI con-` template such variations as may be found desir-- able to adapt .the invention to its intended uses and what I claim and desire to secure by Letters Patent is:

parachute element, a plurality of cords each in engagement with the peripherial portionof said parachute element and secured: at their' inner ends to a uniting member, a cable attached to said parachute element at a central part thereof, pass-- ing through said uniting element'and secured at its inner end to a xed support, a cablewsecured to said uniting member and wound upon a reel,

a spring pressed pawl adapted to engage andhold said reel whereby said'uniting element is secured to said-support, and means o n said pawl' for manual engagement whereby said repel may be released.

2. A device of the. class` described having a parachute element, a plurality of cordseach in` engagement with the peripherial portion of saidl parachute element and `securedat` theirl innerist 1. 'A' device ofthe class Ydescribed Vhaving aV ,gn letz ends to a luniting member, a cable attached to the parachuteelement at a central part V`thereof; passing through said uniting element 'andisecured at itsfinner end Vto a fixed support, a cable having one end secured'to saiduniting member and its other `end wound upon-afreel, ar helical spring to give tension to the reel, a spring pressed pawl adapted -toY engage 5and hold the reel, and

means on the pawl for manual "engagement whereby the reel may be'releasedj 1 f 3. In combination with anaircraft, a' 'parachute, 'a cable having one endV secured tothe parachute. and vthevother end "centrally of the aircraft, a guide for the cable near therear end of the aircraft, a casing for the parachute, means for releasing thef-parachute'from the casing,v

. ing said cover in closed position, an element adapted by lateral movement to withdraw said holding means, means for releasing Vsaid guide,"v

and a lost motion'connection between said element for releasing the holding means and the guide releasing means whereby a partial lateral movement of said means will release the casing and further movement will operate' the guide releasing means; y

5. A device of the class described having a series of parachute elements of graduated sizes adapted to assume a superimposed position, va series of. cords each in engagement with Vthe periphery of the outer parachute element and converging forwardly to connection with each of said other parachute elements at the peripherial por tions thereof and secured at their inner ends to a uniting member, a flexible tube attached to each of said parachute elements other than theelement at the rear and extending rearwardly Atoward the next adjacent element, a cable attached to each of said elements at a central part thereof, passing through said .tubes and'through said uniting element and secured at its inner end to a xed support, means for securing said uniting element relative to said support wherebyl the parachute elements may expose a concave sur--` face to air. currents, and means whereby said se'- curing means may be released and thereby permit said parachute elements to collapse.

6. A device of the character described com` prising a series of parachute elements of graduated sizes adapted to assume a superimposed po.-A

sition, a series of cords each having permanent engagement with the periphery of the cuter par# achute element'and converging forwardly and having sliding engagement with the peripheries of the remaining parachute elements, a uniting member attached. to the forward ends of said cords, a cable attached'to a central part of each of said parachute elements and extending through said unitingmember, a fixed support to Ywhich said cable is secured, a cord connected with said uniting member, and means connected with said last named cord permitting the peripheral portions of said parachute elementsto collapse and extend rearwardly while said central portions are held by said cable.

7. Adevice of thev ,character` described com-' prising atandem seriesl of parachute elements of gradually diminishing sizes from thereartovpermanent engagement with the' peripheryiof the rear parachute elementand `converging 'forwardly and having sliding'engagement with the per'iphe'ries'of the remainingfparachute elements, a .unitingvmember attached tofthe forwardV ends ofsaid cords, a cable attached to va'central' part of each -of- 'saidlpar'achute elements and extending lforwardly through's'aid'uniting member, Va

xedsupport to which the forward end of `said t cable is'attached,ia ycord connected with land extending forwardly frorn said uniting member,

and alreel device'V connected with the forward end of saidflast named cordandl controlling said first namedfcords to permit -the'peripheral-v por.- tions of said parachute elements to collapse and extend rearwardly or tolhold said parachute elements expanded in the'form of parachutes, as

desired. g

8. In an airplanehavingfa fuselage, a parachute element, a series of lcords having permaparachute element and converging forwardly, a cord having its rear end` attached to said rst named cords and its'front end extending above and attached to said fuselage, means in connection with the upper side of the fuselage between theV front end of said second cord and the front ends of said first named cords holding'the .rear portion of said second cord adjacent to the.

upper side ofthe rear vend of the fuselage, and a device for disengaging said means from said second cord. f

9. In an airplane having an elongated fuselage, a series ofparachute elements of graduated'sizes, a series of cords having permanent engagement with the periphery of the outer vparachute elenentv engagement .with theperiphery of said no y ment and converging forwardly and having sliding' engagement with theperipheries of the re- Vmaining parachute elements, a'cord having its rear end connected to the front ends of said first named cords, a device'connecting the front end of said second cord with the fuselage, a cable attached to the central part of each of said rparachute elements, a device connecting thefront end of said cable with .thefuselage adjacent to said'device connecting said second cord with the fuselage, and-means for holding rearward portions of said second cord and said cable in connection with the rear portion of the fuselage.

10. In an; airplane having an elongated fuse,-

lage, a seriesof parachute elements of graduated sizes, a series of cords Vhaving, permanent enfgagementA with the peripheryof the outer parachute element and converging-forwardly and having sliding engagement with the peripheries of' the remaining parachute elements; a cord having its rear end Vconnected tothe front ends of said first named cords, a device connecting the front 'end of said second cord with the. fuselage, a

cable attached to the central part of each of said parachute elements, a device connecting the front end of said cable with the fuselage adjacent to said device connecting said second cord'with the fuselage, means for holding rearward portions of said second cord and said cable in connection ,with the rear portion of the fuselage, and consnections for releasing said means from said sec# ondrcord and said cable.

11; InV an airplane having a fuselage," a parai .chute element, vra flexible connection', flexible means connecting said parachute element with an ,intermediate upperportion of said fuselage,.Y vand a releasabledevice kconnecting saidV flexible means with the rear upper portion of the fuse,-`

,fuselage to retard the forward movement of the airplane. v

14. In an airplane having a fuselage, a series of parachute elements, exible means connecting said parachute elements with an intermediate upper portion of the fuselage, avreleasable device for holding said flexible means in connection with the rear; upper portion of the fuselage to retard the forward movement of the airplane, and connections for disengaging said devices from said flexible means t-o permit said parachute elements to extend vertically from the intermediate portion of the fuselage.

- HARRY E. HONEYWELL. 

